US 12,410,724 B1
Gas turbine engine with inertially damped seals
Uttara Vijay Kumar, Rexford, NY (US); Deepak Trivedi, Halfmoon, NY (US); Rahul Anil Bidkar, Clifton Park, NY (US); and Steven Douglas Johnson, Milford, OH (US)
Assigned to General Electric Company, Evendale, OH (US)
Filed by General Electric Company, Cincinnati, OH (US)
Filed on Jul. 31, 2024, as Appl. No. 18/789,987.
Int. Cl. F01D 11/02 (2006.01); F01D 25/04 (2006.01)
CPC F01D 11/025 (2013.01) [F01D 25/04 (2013.01); F05D 2240/55 (2013.01); F05D 2260/96 (2013.01)] 17 Claims
OG exemplary drawing
 
1. A gas turbine engine comprising:
a compressor section and a turbine section in axial flow arrangement defining an axially extending, longitudinal centerline, and arranged as a rotor and a stator; and
a floating seal assembly disposed at an interface of the rotor and the stator, the floating seal assembly comprising one or more inertial damping elements tuned to one or more frequencies, wherein at least one inertial damping element of the one or more inertial damping elements comprises:
one or more tubes, wherein the one or more tubes the one or more tubes comprising a plurality of tube segments, wherein at least one of the plurality of tube segments extends perpendicularly to the floating seal assembly; and
a fluid disposed within the one or more tubes.